Results
76-07-13: 76-07-13 HAMBURGER FLUGZEUGBAU GmbH: Amendment 39-2579. Applies to Model HFB-320 airplanes, S/N 1021 thru 1023, 1026 thru 1028, 1030 thru 1040, 1045, and 1049 thru 1057, certificated in all categories. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To detect possible incorrect adjustment of camlocks that could result in cracking of the camlock housing, possible inadvertent opening of the door, and inflight explosive decompression, accomplish the following: (a) Inspect the camlocks for correct adjustment in accordance with the accomplishment instructions contained in Section B, Part 1, of HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent. (b) If a camlock is found out of adjustment beyond the tolerances specified in HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976,or an FAA-approved equivalent, rectify the camlock adjustment in accordance with the accomplishment instructions contained in Section B, Part 2, of Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent. (c) Inspect the door frame camlock housings, which house the camlocks for which adjustment is required in accordance with paragraph (b) of this AD, for cracks, using a dye penetrant method in accordance with the instructions contained in Section B, Part 3, of HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent. (d) If any cracks are found in the door frame camlock housing during the inspection required by paragraph (c) of this AD, before further flight, except that the aircraft may be flown unpressurized in accordance with FAR's 21.197 and 21.199 to a base where the replacement can be accomplished, replace the camlock housing with a new part of the samepart number. This amendment becomes effective, April 26, 1976.
2013-22-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 series airplanes. This AD was prompted by reports of fasteners missing on an airplane undergoing a passenger- to-freighter conversion. This AD requires doing a general visual inspection of the station 1920 splice clip for correct fastener installation, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct missing or incorrect fasteners, which can lead to cracking and loss of load carrying capacity, resulting in a possible decompression event.
90-21-03: 90-21-03 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-7072. Docket No. 90-ASW-44. Final Rule of Priority Letter AD 90-21-03. Applicability: All BHTI Model 206A, 206A-1, 206B, 206B-1, 206L, 206L-1 and 206L-3 helicopters, certificated in any category, with tail rotor blade assembly, P/N 206-016-201-125 or - 127. Compliance: Required before further flight, unless already accomplished. To prevent the loss of a tip weight, failure of the tail rotor blade assembly, loss of the tail rotor hub assembly and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, inspect the aircraft to determine the part number and serial number of the installed tail rotor blade assembly. If P/N 206-016-201-125 or -127 with a serial number listed below is installed on the helicopter, remove and replace the assembly with an airworthy blade assembly. For 206-016-201-127 T/R BLADE CS-0203 CS-0206 CS-0238 CS-0985 CS-1141 CS-1153 CS- 1207 CS-1210 CS-1219 CS-1229 CS-1232 CS-1235 CS-1252 CS- 1304 CS-1306 CS-1316 CS-1325 CS-1332 CS-1337 CS-1342 CS- 1351 CS-1354 CS-1359 CS-1360 CS-1368 CS-1373 CS-1375 CS- 1380 CS-1391 CS-1461 CS-1466 CS-1476 CS-1489 CS-1519 CS- 1523 CS-1524 CS-1525 CS-1528 CS-1533 CS-1544 CS-1553 CS- 1555 CS-1556 CS-1557 CS-1559 CS-1563 CS-1564 CS-1566 CS- 1577 CS-1579 CS-1580 CS-1584 CS-1585 CS-1588 CS-1594 CS- 1597 CS-1599 CS-1612 CS-1614 CS-1635 CS-1642 CS-1647 CS-1656 CS-1670 CS-1673 CS-1685 CS-1705 CS-1716 CS-1726 CS- 1733 CS-1734 CS-1737 CS-1740 CS-1744 CS-1745 CS-1754 CS- 1756 CS-1760 CS-1771 CS-1778 CS-1784 CS-1827 CS-1830 CS- 1842 CS-1844 CS-1855 CS-1856 CS-1881 CS-1890 CS-1893 CS- 1894 CS-1900 CS-1901 CS-1907 CS-1909 CS-1913 CS-1914 CS- 1940 CS-1944 CS-1953 CS-1957 CS-1958 CS-1958 CS-1959 CS- 1961 CS-1978 CS-1979 CS-1981 CS-1982 CS-1983 CS-1985 CS- 1986CS-1989 CS-1994 CS-1997 CS-1998 CS-2000 CS-2003 CS- 2007 CS-2016 CS-2019 CS-2027 CS-2033 CS-2037 CS-2088 T-47310 T-47361 T-47371 T-47378 T-47397 T-47398 T- 47401 T-47426 T-47458 For 206-016-201-125 T/R BLADE CS-136 CS-158 CS-398 CS-534 CS-625 CS-658 CS- 684 CS-685 CS-688 CS-690 CS-711 CS-715 CS-716 CS- 719 CS-720 CS-738 CS-740 CS-752 CS-807 CS-832 CS- 865 CS-871 CS-874 T-61995 (b) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This amendment (39-7072, AD 90-21-03) becomes effective on August 14, 1991, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 90-21-03 issued October 5, 1990, which contained this amendment.
91-26-02: 91-26-02 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 8113. Docket No. 91-NM-183-AD. Applicability: Model DHC-8-102 and -103 series airplanes, serial numbers 3 through 287, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced engine-out takeoff and climb performance of the airplane, accomplish the following: (a) Within 7 days after the effective date of this AD, remove Supplement No. 21, dated May 30, 1990 (for Model DHC-8-102 series airplanes), or September 26, 1990 (for Model DHC-8-103 series airplanes), from the de Havilland Airplane Flight Manual PSM 1-81-1A. (b) Within 7 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) by inserting the following statement. This may be accomplished by inserting a copy of this AD into the AFM. "Supplement No. 21, dated May 30, 1990 (for Model DHC-8-102 series airplanes), or September 26, 1990 (for Model DHC-8-103 series airplanes), of the de Havilland Airplane Flight Manual PSM 1-81-1A, is withdrawn. Use of engine bleed air during takeoffs and landings is prohibited." (c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (e) This amendment (39-8113, AD 91-26-02) becomes effective on December 23, 1991.
2013-21-02: We are superseding airworthiness directive (AD) 2012-24-09 for Lycoming Engines TIO-540-AK1A, and Continental Motors, Inc. (CMI) TSIO- 360-MB, TSIO-360-SB, and TSIO-360-RB reciprocating engines, with certain Hartzell Engine Technologies (HET) turbochargers, model TA0411, installed. AD 2012-24-09 required removing certain HET turbochargers from service before further flight. This AD also requires removing certain HET turbochargers from service before further flight. This AD was prompted by a report that an additional engine, the CMI LTSIO-360- RB, has the affected HET turbochargers installed. We are issuing this AD to prevent turbocharger turbine wheel failure, reduction or complete loss of engine power, loss of engine oil, oil fire, and damage to the airplane.
51-11-01: 51-11-01 MARTIN: Applies to All Models 202 and 202A Airplanes Except as Noted. Compliance required as specified herein. Compliance with this note cancels the requirements of AD 50-41-02. In order to comply with the recommendations of the Martin 202 Modification Board, the following items must be accomplished. In all cases, modifications which are demonstrated to provide a level of safety equivalent to that provided by the modifications listed herein will be acceptable in lieu of the listed modifications. Compliance required by August 16, 1951. 1. Decrease breaker rating for propeller anti-icing circuit to 5 amperes to accommodate No. 20 wire. (Applies to Model 202 airplanes only.) 2. Install negative pressure scoop on battery vent line. Compliance require by November 16, 1951. 1. Add manually operated charging valve in the emergency brake hydraulic system in accordance with Glenn L. Martin Co. Service Bulletin No. 185. Compliance required by December 1, 1951. 1. Provide circuit protection for voltmeter. 2. Provide circuit protection at main bus for generator tip light circuit. 3. Provide circuit protection for ammeter wires. Compliance required by February 1, 1952. 1. Install circuit breaker in circuit breaker panel with wire routed back to auxiliary bus control relay.
2013-20-09: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-215-6B11 (CL-415 Variant) airplanes. This AD requires replacing the panel assembly of the main distribution center (MDC) rack. This AD was prompted by findings of chafed power wires due to flexing of the MDC rack panel. We are issuing this AD to prevent damage to power wires, which could cause simultaneous loss of systems such as electrical power, pilot indications, and caution/advisory lighting systems, which are essential for safe flight.
2013-03-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of cracking through the honeycomb core closed with phenolic resin. This condition could result in extended debonding and could adversely affect the structural integrity of the rudder. This AD requires inspecting to determine the serial number of a certain rudder and replacing the rudder with a new or serviceable rudder if necessary. We are issuing this AD to prevent extended de-bonding, which could result in loss of the rudder and consequent reduced controllability of the airplane.
77-21-06: 77-21-06 PIPER: Amendment 39-3058. Applies to Models PA-25, PA-25-235 and PA-25-260, Serial Nos. 25-1 and up, certificated in all categories. To prevent weakening of the fuselage steel tubing cluster in the area of the rear wing spar attachment due to corrosion of the fuselage tubing, accomplish the following: (a) Within the next 30 days in service after the effective date of this AD or upon the attainment of a total of 1 year in service, whichever occurs later, unless previously accomplished within the last year and at intervals not to exceed 1 year from the last inspection, inspect the fuselage steel tubing cluster in the area of the rear wing spar attachment and repair if necessary, in accordance with the "Instructions" section of Piper Service Bulletin No. 551 dated April 22, 1977, or equivalent. The aircraft may be flown in accordance with FAR 21.197 to a base where inspection and repair can be made. (b) Equivalent inspections and repairs must be approved bythe Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD. This amendment is effective October 19, 1977.
2013-19-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SP series airplanes. This AD was prompted by reports of worn or incorrectly assembled latches on main deck escape slides installed on airplane doors. This AD requires determining if the latches are correctly assembled; and doing corrective actions if necessary. This AD also requires, for certain airplanes, modifications to the escape slide/rafts and escape slides. We are issuing this AD to prevent a latch hook moving from closed to open in an escape slide/raft or escape slide, which could result in the escape slide/raft or escape slide not deploying correctly in an emergency, or releasing/inflating into the passenger cabin and causing injury to passengers and crew.
91-24-03: 91-24-03 PRATT & WHITNEY CANADA: Amendment 39-8088. Docket No. 91-ANE-36. Supersedes AD 90-24-05, Amendment 39-6812. Applicability: Pratt & Whitney Canada (PWC) PW123, PW124B, PW125B, and PW126A turboprop engines installed on but not limited to DeHavilland Dash 8 Series 300, Aerospatiale ATR72, Fokker 50, and British Aerospace ATP aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent a low pressure turbine (LPT) overspeed, that could result in uncontained disk failure, and subsequent damage to the aircraft, accomplish the following: (a) For PW123 and PW124B engines that have not been modified in accordance with any revision level of PWC Service Bulletin (SB) 21018, prior to the effective date of this AD, accomplish the following: (1) Within 5 days after the effective date of this AD, perform a turbomachinery magnetic chip detector (MCD) continuity check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991. (2) Within 5 days after the effective date of this AD, perform a turbomachinery MCD functional check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991. (3) Thereafter, at intervals not to exceed 25 flight hours since last inspection, perform the turbomachinery MCD continuity check specified in paragraph (a)(1) of this AD. (4) Thereafter, at intervals not to exceed 300 flight hours since last inspection, perform the turbomachinery MCD functional check specified in paragraph (a)(2) of this AD. (b) In addition to the requirements of paragraph (a) of this AD, for PW123 engines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, accomplish the following: (1) Within 5 days after the effective date of this AD, perform a turbomachinery MCD airframe circuitry check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991. (2) Thereafter, at intervals not to exceed 300 flight hourssince last inspection, perform the turbomachinery MCD airframe circuitry check specified in paragraph (b)(1) of this AD. (c) For PW125B and PW126A engines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, accomplish the following: (1) Within the next 125 flight hours after the effective date of this AD, unless previously accomplished within the last 875 flight hours, perform a turbomachinery MCD operational check in accordance with the applicable engine maintenance manual. NOTE: Further information on the turbomachinery MCD operational check specified in paragraph (c)(1) can be found in PWC Maintenance Manual Part Number 3034932 for the PW125B, and PWC Maintenance Manual Part Number 3034922 for the PW126A. (2) Within the next 125 flight hours after the effective date of this AD, unless previously accomplished within the last 875 flight hours, perform an operational check of the turbomachinery MCD airframe circuitry and indicating system in accordance with the applicable aircraft maintenance manual. NOTE: Further information on the turbomachinery MCD airframe circuitry and indicating system specified in paragraph (c)(2) of this AD can be found in Fokker 50 Maintenance Manual, Chapter 77-33-00, for the PW125B, and BAe ATP Aircraft Maintenance Manual, Chapter 79-33-00, for the PW126A. (3) Thereafter, at intervals not to exceed 1,000 flight hours since last inspection, perform the turbomachinery MCD operational check specified in paragraph (c)(1) of this AD. (4) Thereafter, at intervals not to exceed 1,000 flight hours since last inspection, perform the operational check of the turbomachinery MCD airframe circuitry and indicating system in paragraph (c)(2) of this AD. (d) The initial inspections of paragraphs (a)(1), (a)(2), and (b)(1) of this AD need not be accomplished for those PW123 and PW124B engines previously inspected in accordance with AD 90-24-05. (e) Forengines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, incorporate a new low pressure rotor balancing assembly in accordance with PWC SB 21018, Revision 2, dated November 25, 1991, at the next engine shop visit or by June 30, 1994, whichever occurs first. The incorporation of a new low pressure rotor balancing assembly in accordance with this paragraph constitutes a terminating action for paragraphs (a), (b), or (c), as applicable, of this AD. (f) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into a maintenance facility for the conduct of any type of maintenance. (g) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Engine Certification Office. (h) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (i) The inspections and modifications shall be done in accordance with the following Pratt & Whitney Canada service documents: Document Number Page Number Issue/Rev Date PWC SB 21018R2 1-36 Revision 2 11/25/91 Total: 36 pages PWC SB 20938R2 1-8 Revision 2 11/18/91 Total: 8 pages This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Pratt & Whitney Canada, Technical Publications Department, 1000 Marie Victorin, Longueuil, Quebec J4G 1A1. Copiesmay be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (j) This amendment becomes effective on May 26, 1992.
78-03-01: 78-03-01\tBELL 47 SERIES AS MODIFIED BY STC SH357SW: Amendment 39- 3131. To preclude failure of the hopper upper support bracket, accomplish the following: \n\n\tWithin the next 25 hours flight time and at each 25 flight hours thereafter, inspect the hopper upper support bracket (P/N B630224) for cracks and/or deformation. If cracks and/or deformation are found, replace or repair. Inspections may be discontinued upon installation of Simplex Modification No. E201 (See Fig. 1), or equivalent modification or repair approved by an FAA Maintenance Inspector. \n\n\tThe manufacturer's repair, identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received the repair documents from the manufacturer, may obtain copies upon request to Simplex Manufacturing Company, 5224 N.E. 42nd Avenue, Portland, Oregon 97218. This repair document may also be examined at FAA Northwest Region, 9010 E. Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective March 6, 1978.
2013-19-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of chafing damage to a wire bundle that was arcing to hydraulic tubing and caused by insufficient separation between the wire bundle and the hydraulic tubing in the main landing gear (MLG) wheel well. This AD requires an inspection for damage of wire bundles and hydraulic tubing on the right side of the forward bulkhead of the MLG wheel well; installation of new clamps; and corrective actions, as applicable. We are issuing this AD to detect and correct possible damage caused by insufficient separation between the wire bundles and hydraulic \n\n((Page 59799)) \n\ntubing to prevent electrical arcing in a flammable fluid leakage zone, which could lead to a wheel well fire.
90-09-10: 90-09-10 TEXAS INSTRUMENTS: Amendment 39-6565. Docket No. 89-ANE-38. Applicability: To circuit breaker Models 6TC6-7.5 and -10 and 6TC20-7.5 and -10, all with date codes 8150 and earlier. Compliance is required no later than November 1, 1990, unless already accomplished. (a) To prevent potential overheating of the applicable circuit breakers, replace Texas Instruments circuit breaker Models 6TC6-7.5 and -10 and Models 6TC20-7.5 and -10, all with date codes 8150 and earlier. These circuit breakers may be replaced with the same model numbers with the manufacturing date codes of 8151 and later. NOTE: The circuit breakers are installed in, but not limited to, aircraft manufactured by Boeing Commercial Airplanes and Lockheed Corporation. Service bulletins published to date, which may be helpful in identifying replacement circuit breakers, are as follows: (1) The Boeing Commercial Airplanes' service bulletins 757-24-0054, 747-24-2135, and 767-24-0060, all dated August 31, 1989. Their part numbers BACC18AC7 and BACC18AC10 are used to identify Texas Instruments Model 6TC6-7.5 and 6TC6-10, respectively. (2) The Lockheed Corporation service bulletin 093-24-134, dated August 12, 1987. Their part numbers LS10159-7 and LS10159-10 are used to identify Texas Instruments Model 6TC20-7.5 and 6TC20-10, respectively. (b) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment (39-6565, AD 90-09-10) becomes effective on May 30, 1990.
57-12-02: 57-12-02 BELL: Applies to Model 47H1 Helicopters Serial Numbers 1349, 1351 Through 1360, 1362, 1363, 1365 Through 1371. Compliance required as soon as possible but not later than August 1, 1957. In order to prevent possible failure of the tail boom attach bolts the following inspection and rework should be accomplished. 1. Visually inspect the four (4) tail boom attach fittings 47-265-026-1 and -2 on the forward bulkhead to determine if all eight (8) bolt hole locations (2 in each fitting) have been spot faced. It is necessary to remove the baggage compartment floor section in order to make this inspection. 2. If it is found that any or all the bolt hole locations have not been spot faced, it is required that they be spot faced in accordance with the instructions given in Bell Mandatory Service Bulletin No. 116, dated November 9, 1956.
2013-19-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes. This AD was prompted by a report that a certain wire harness located in the tail cone has wiring of a narrower gauge than design requires. This AD requires replacing the affected wire harness. We are issuing this AD to prevent damage to the affected wiring, which could create an ignition source in an area that might contain fuel vapors, possibly resulting in an uncontrolled fire and subsequent loss of the airplane.
2013-16-03: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350 and AS355 helicopters, to require inspecting for a crack in the control lever attachment yokes, and if needed, replacing the tail rotor gearbox (TGB). This AD is prompted by improper casting of TGB casing assemblies, which may lead to cracking. A crack in the control lever attachment yokes could cause a loss of tail rotor pitch control, and consequently, loss of control of the helicopter.
2012-12-13: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD was prompted by reports of baggage bay fire bottles that can be misassembled such that two squib electrical connectors can be cross- connected. This AD requires a general visual inspection of certain baggage bay fire bottles for correct connection and for the length of the wiring loom, modification of the wiring loom to certain squib connectors, and corrective actions if necessary. We are issuing this AD to detect and correct excessive wiring loom length and improper connection of the squib connecters, which in conjunction with a fire in one of the baggage bays, could result in the fire extinguishing agent being discharged into a wrong compartment and consequent damage to the airplane.
78-07-02: 78-07-02 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-3168. Applies to Model HS-125 Series 700A airplanes, S/N NA0201 through NA0210, certificated in all categories. Compliance is required as indicated. To detect cracking and possible failure of the attaching lugs of the tee pieces, P/N 25- 7PA41, that are mounted on the master refuel valve, accomplish the following: (a) Within 10 days after the effective date of this AD, unless already accomplished, inspect the attachment lugs for cracking and the area of attachment to the main refuel valve for evidence of fuel leakage in accordance with Part A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd. Alert Service Bulletin 28-A65, dated November 30, 1977 (service bulletin), or an FAA-approved equivalent. (b) If during the inspection required by paragraph (a) of this AD, evidence of lug cracking or fuel leakage is found, before further flight, except that the airplane may be flown in accordance with FARs 21.197 and 21.199 to a base where the repairs can be performed, remove and destroy both tee pieces and replace with the improved parts, P/N 25-7PA125A, in accordance with Part B of the section entitled "Accomplishment Instructions" of the service bulletin, or an FAA-approved equivalent. (c) If during the inspection required by paragraph (a) of this AD, no evidence of lug cracking or fuel leakage is found, continue to inspect the area in accordance with paragraph (a) of this AD, at intervals not to exceed three calendar months from the initial inspection, except that both tee pieces must be replaced in accordance with the installation instructions of paragraph (b) of this AD no later than August 1, 1978. Compliance with the repetitive inspection requirements of this paragraph may be terminated after the replacement required by this paragraph is accomplished. This amendment becomes effective April 14, 1978.
2013-18-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters with certain fire extinguishing systems installed. This AD requires modifying the fire extinguishing system injection tubes. This AD is prompted by a report that the injection tubes are deforming due to heat. The actions required by this AD are intended to prevent deformation of the fire extinguishing system injection tubes during a fire, which could result in impaired distribution of the fire extinguishing agent, failure of the fire extinguishing system to contain an engine fire, and subsequent loss of control of the helicopter.
77-17-03: 77-17-03 BELL: Amendment 39-3009. Applies to Model 212 helicopters, S/N 30502 through 30804, 30806 through 30810, 30812, 30814, 30815, 30817, 30818, 30820 through 30825, 30827, 30828, 30829, and to Model 205A-1 helicopters, S/N 30001 through 30247, equipped with tail rotor blades, P/N 212-010-750, certificated in all categories. Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. To detect possible cracks in each tail rotor blade pitch change horn, P/N 212-010-716-5 and -9, accomplish the following: (a) Remove the bolt and barrel nut of the control rod and clean the external surfaces of the pitch change horns. (b) Inspect the horns for cracks, particularly in the barrel nut and bushing area using a dye penetrant or equivalent inspection method. (c) If a crack is found, replace the affected pitch change horn before further flight in accordance with the Model 212 Overhaul Manual, paragraphs 65-58 and 65-63, or Models 205A/205A-1 Maintenance and Overhaul Instructions, paragraphs 3-41 and 3-43, as appropriate. (d) Install the blade's control rod bolt and barrel nut as specified in the instructions in paragraphs 65-57 Model 212 Maintenance Manual or 3-40 Models 205/205A-1 Maintenance and Overhaul Instructions, as appropriate. (e) After installation of pitch change horns, P/N 212-010-716-11, this AD is no longer applicable. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (g) The manufacturer's instructions identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Textron, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. (Bell Helicopter Textron Service Bulletin Nos. 212-77-7 and 205-77-5 dated March 11, 1977, pertain to this subject.) This amendment becomes effective August 19, 1977.
76-13-06: 76-13-06 DEHAVILLAND: Amendment 39-2654. Applies to DeHavilland Model DHC- 6 series Twin Otter aircraft serial nos. 1 thru 430 incorporating wing tip strobe lighting. Compliance required as indicated: To restore the aircraft lightning strike protection to its original status, as a result of excessive removal of lightning strike protection bonding strap material, during the installation of the wing tip strobe lights, accomplish the following: (a) Within the next 100 hours in service after the effective date of this AD, accomplish the alteration to the aircraft wing tips in accordance with "Accomplishment Instructions" in DeHavilland DHC-6 Service Bulletin No. 6/318, dated January 3, 1975, or later revision, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective July 6, 1976.
2013-16-24: We are superseding airworthiness directive (AD) 90-23-14 for certain The Boeing Company Model 747 series airplanes. AD 90-23-14 required inspections of the fuselage skin lap splice between body station (BS) 340 and BS 400 at stringers (S)-6L and S-6R, and repair if necessary. This new AD adds new repetitive inspections for cracking in the S-6 skin lap splice, which terminates the inspections required by AD 90-23-14; eventual modification of the lap splice, which terminates the repetitive inspections; post-modification inspections; and corrective actions if necessary. This AD also adds airplanes to the applicability. This AD was prompted by a report of cracks up to 18.5 inches that were found at S-6L and S-6R on several airplanes, and subsequent analysis results that indicated that the protruding head fastener modification and related post-modification inspections required by AD 90-23-14 are not adequate to prevent cracking at the upper row of fasteners in the S-6 lap joint before the cracks reach a critical length. We are issuing this AD to detect and correct cracking at the upper row of fasteners in the S-6 lap joint, which could result in a sudden loss of cabin pressurization and the inability of the fuselage to withstand failsafe loads.
77-15-15: 77-15-15 BRITISH AIRCRAFT CORPORATION: Amendment 39-2986. Applies to BAC 1- 11 200 and 400 series airplanes, certificated in all categories. Compliance is required within the next 200 hours time in service after the effective date of this AD, unless already accomplished. To prevent the inadvertent loss of cabin pressure due to failure of the light alloy stop on the cabin pressure discharge valve manual control, replace the light alloy stop, P/N AB55-2301, on the gear wheel and drum assembly of the air conditioning discharge valve manual control (P/N AB55A-2425 or ED55A779) with an improved strength stop, P/N AB55-3433, or an FAA-approved equivalent. (British Aircraft Corporation Service Bulletin No. 21-PM 5139, Revision 2, dated September 5, 1973, applies to this same subject.) This amendment becomes effective August 29, 1977.
51-03-01: 51-03-01 MOONEY: Applies to Model M-18 Series Aircraft, Serial Numbers 1 Through 82 and 201 Through 236. Compliance required not later than March 15, 1951. There have been reported failures of the fuel line due to vibration and relative motion between the fuel tank and the fuel shutoff valve. To preclude the possibility of recurrence of this type failure, cut the fuel line at a point approximately 4 inches from the fuel tank outlet and install a 4-inch length of 3/8-inch ID approved aromatic resistant flexible hose and hose clamps at this point. (Mooney Service Bulletin No. 6 covers this same subject.)